MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL

The following list of Manufacturers and/or publicatio~ns can provide servicing and maintenance information on com- ponents of the Mooney, Model M20R No avionics equipment Manufacturers or publications are listed due to the many configurations that can be installed in the airdraft. These can be obtained from the repair stations for a par- ticular avionics manufacturer. Any publications available from Mooney Aircraft Corporation are listed in the Parts Price List and are available through any Mooney Service Center. Most manufa4turer/vendor publications are not availabel through Mooney Air- craft Corporation, these should be obtained from the applicable ManufacturerNendor. As publications on various components become available, they will be added to the list below. VENDOR ADL~RESSES PUBLICATIONS ENGINE PUBLICATIONS The following maintenance publications can be obtgined through Teledyne Continental Motors, Aircraft Products, P.O. Box 90, Mobile, Alabama, USA, 36601, Attn: Accounts Receivable (Prepaid only). Overhaul Manual for Teledyne Continental Motors Aircraft 10-550 Engine Models, Fom~ X30568A. Illustrated Parts Catalog for Teledyne Continental Motors 10-550 series aircraft engines, Form X30569A. Maintenance Operators Manual for Teledyne Coritinental Motors 10-550 aircraft engines, Form X30565. Service Bulletins Specify model of engine for which maintenance data is desired when ordering. Fuel Injector Manual, Form X30593A ACCESSORY PUBLICATIONS PROPELLER BAcCauley Propellers Obtain publications from McCauley Accessories Division, 3535 McCauley Drive, Vandalia, OH.,45377. Service Manual No. 761001 for McCauley C400 series constant speed propellers. MAGNETO Teledyne Continental Motors, Aircraft Products, P.b. Box 90, Mobile, Alabama, USA, 36601, Attn: Publications Dept., for TCM (Bendix), Type S6RN-25 Series magnetos. ALTERNATOR Alternator Service Instructions, Form X30531-3, Teledyne Continental Motors, Aircraft Products, P.O. Box 90, Mo- bile, Alabama, USA, 36601, Attn: Publications Dept. STARTER Service Manual, Teledyne Continental Motors, Aircraft Products, P.O. Box 90, Mobile, Alabama, USA, 36601, Attn: Publications Dept FUEL PUMP (Engine Driven) Teledyne Continental Motors, Aircraft Products, P.O. Box 90, Mobile, Alabama, USA, 36601, Attn: Publications Dept IGNITION SYSTEM Master Service Manual, TCM Ignition Systems and Components, Form X40000, Teledyne Continental Motors, Air- craft Products, P.O. Box 90, Mobile, Alabama, USA, 36601, Attn: Publications Dept IPrecise Flight, Inc., 63120 Powell Butte Rd., Bend, OR 97701, Telephone: (503) 382-8684 SPEED BRAKES INTRODUCTION Rev. 8-95 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL CHAPTER- SECTION- TITLE INDU(GUIDE CHAPTER SECTION TITLE 1 4 RESERVED MAY BE USED LATER 5 TIME LIMITS/MAINTENANCE CHECKS 00 GENERAL 10 TIME LIMITS 20 SCHEDULED MAINTENANCE CHECKS 6 DIMENSIONS AND AREAS 00 GENERAL 7 LIFTING 10 JACKING 8 LEVELING AND V~EIGHING 00 LEVELING 9 TOWING AND TAXIING 00 GROUND HANDLING 10 TOV\nNG 20 TAXIING 30 EMERGENCY PROCEDURES 10 PARKING AND MOORING 00 GENERAL 10 PARKING 20 MOORING 11 PLACARDS AND MARKINGS 00 GENERAL 10 MARKINGS 20/30 PLACARDS- UC~ERIOWINTERIOR 12 SERVICING 00 SERVICING 10 REPLENISHING 20 SCHEDULED SERVICING 20 STANDARD PRACTICES -AIRFRAME 00 GENERAL 21 ENVIRONMENTAL SYSTEMS 00 CABIN VENTILATION SYSTEM 40 HEATING 50 COOLING 60 TEMPERATURE CONTROL 24 ELECTRICAL POWER 00 GENERAL 30 DC GENERATION 40 EXTERNAL POV~R 50 ELECTRICAL LOAD DISTRIBUTION REV.8-95 INTRODUCTION Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER SECTION TITLE 25 EQUIPMENT/FURNISHING THIS SECTION MAY NOT BE INCLUDED 1N THIS S 8 M. 00 GENERAL 10 FLIGHT COMPARTMENT 20 PASSENGER COMPARTMENT 50 CARGO COMPARTMENT 60 EMERGENCY EQUIPMENT 70 ACCESSORY COMPARTMENT 27 FLIGHT CONTROLS 00 GENERAL 10 AILERON SYSTEM 20 RUDDER SYSTEM 30 ELEVATOR SYSTEM 40 STABILIZER TRIM SYSTEM 50 WING FLAP SYSTEM 60 INTERCONNECT 90 MISCELLANEOUS 28 FUEL 00 GENERAL 10 STORAGE 20 DISTRIBUTION 30 DUMP 40 INDICATING 90 MISCELLANEOUS 30 ICE AND RAIN PROTECTION 00 GENERAL 10 AIRFOIL 30 PITOT AND STATIC 40 WINDSHIELDS 60 PROPELLERS 32 LANDING GEAR 00 GENERAL 10 MAIN LANDING GEAR AND DOORS 20 NOSE LANDING GEAR AND DOORS 30 EXTENSION AND RETRACTION 40 WHEELS AND BRAKES 50 STEERING 60 POSITION AND WARNING 80 MISCELLANEOUS 33 LIGHTS 00 GENERAL 10/20 INTERIOR LIGHTS MAINTENANCE PRACTICES 40 EXTERIOR LIGHTS MAINTENANCE PRACTICES 34 NAVIGATION 00 GENERAL 10 PITOT 8 STATIC AIR PRESSURE SYSTEM 20 DIRECTIONAL GYRO COMPASS INTRODUCTION REV. 10-98 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL CHAPTER SECTION TITLE 39 ELECTRICAL PANELS AND COMPONENTS 00 GENERAL 10 INSTRUMENT AND CONTROL PANELS 20 ELECTRICAL AND ELECTRONICS EQUIPMENT RACKS 51 STRUCTURES 00 GENERAL 10 STRUCTURAL REPAIR GENERAL 52 DOORS 00 GENERAL 10 CABIN DOOR MAINTENANCE PRACTICE 30 BAGGAGE COMPARTMENT DOOR MAINTENANCE PRACTICE 53 FUSELAGE 00 GENERAL 10 MAIN FRAME ’20 AUXILIARY STRUCTURE 30 PLATES/SKIN 40 ATTACH FITTINGS 50 FILLETS/FAIRINGS 55 STABILIZERS 00 GENERAL 10 HORIZONTAL STABILIZER 20 ELEVATOR 30 VERTICAL STABILIZER 40 RUDDER 56 WINDOWS 00 GENERAL 20 WINDSHIELD CABIN WINDOWS 50 PLEXIGLASS DRILLING 57 WINGS 00 GENERAL 30 PLATES/SKINS 40 ATTACH FITTINGS 50 FLIGHT SURFACES 60 STANDARD PRACTICES PROPELLERS 61 PROPELLERS 00 GENERAL 10 PROPELLER ASSEMBLY 20 CONTROLLING 71 POWERPLANT 00 GENERAL 10 COWLING INTRQDUCTIQN Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER SECTION TITLE 72 ENGINE -RECIPROCATING 00 GENERAL 73 ENGINE FUEL SYSTEM 00 GENERAL 10 DISTRIBUTION 20 CONTROLLING 30 INDICATING 74 IGNITION 00 GENERAL 10 POWER CONTROL 20 EMERGENCY SHUTDOWN 76 ENGINE CONTROLS 00 GENERAL 10 POWER CONTROLS RIGGING 77 ENGINE INDICATING 00 GENERAL 10 POWER 20 TEMPERATURE EXHAUST 00 GENERAL 10 INSTALLATION 30 EXHAUST SYSTEM 40 REPLACEMENT COMPONENTS 79 OIL 00 GENERAL 10 STORAGE 20 DISTRIBUTION 30 INDICATING 80 STARTING 00 GENERAL 10 CRANKING oo TURBINES/EXHAUSTGENERAL 91 SCHEMATICS 00 GENERAL 20 ELECTRICAL SYSTEM HARDWARE CHARTS 30 SCHEMATICS 95 SPECIAL EQUIPMENT INTRODUCTION Rev. 4-95 Island Enterprises CHAPTER TIME LIMITS/ MAINTENANCE CH EC KS Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL CHAPTER 5 TIME LIMITS/MAINTENANCE CHECKS TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 5-00-00 General 5 5-00-01. Landing Gear System 5 5-00-02. Flight Control Systems 5 5-00-03. W~ng FlapSystems 5 5-00-04. Electric Power System 5 5-00-05. Instruments 5 5-00-06. Cabin Heating 3 Ventilating Systems 5 5-00-07. Fuel System 5 5-10-00. Time Limit Components 5 5-10-01 Overhaul and Replacement Schedule 6 5-20-00. Schedule Maintenance Checks 7 5-20-01 Check Points, Torque Values 7 5-20-02 Aircraff File Inspection. 11 5-20-03 Engine FunctionalCheck 11 5-20-04 First 25 Hour Inspection 11 5-20-05 50 Hour Inspection 11 5-20-06 100 Hour Inspection 12 5-20-07 Access Cover Identification, Lubrication and Service Guide 15 REV. 10-98 5-CONTENTS 3/4BLANK Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 5 TIME LIMITS/MAINTENANCE CHECKS LIST OF EFFECTIVE PAGES CHAPTER SECTI ON SUBJECT. PAGE DATE ti-Effectivity 1/2BLANK 10-98 3/4BLANK 10-98 5-Contents 6-94 5-00-00 5. 5-10-00 6 10-98 5-20-01 7 10-98 5-20-01 8. 6-94 5-20-01 9. 6-94 5-20-01 10 10-98 5-20-02 ?1 10-98 5-20-06 12 10-98 5-20-06 13 10-98 5-20-06 14 10-98 5-20-06 15 10-98 16 6-94 5-20-06 10-98 5-20-07 17 5-20-07 18 10-98 5-20-07 19 10-98 5-20-07 20 10-98 REV. 10-98 5-EFFECTIVIN 1MBLANK Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION 5-00-00 -GENERAL i. The Master Switch and power relay control the AIRCRAFT DESCRIPTION. The M20R series of electrical power system, comprised of a 100 AMP, 28 aircraft are four place, high-performance, normally Volt, altemator and two 10 AMP HR, 24 Volt, batteries. aspirated, single-engine, low-wing monoplanes. The The alternator system has an overvoltage protective all-metal airframe has a tubular-steel cabin frame relay and an overvoltage annunciator light. Circuit covered with nonstructural aluminum skins, a breakers or circuit breaker switches protect the semi-monocoque tailcone, and a full-cantilever, electrical wiring and equipment from overloads. laminar-flow wing. Control surfaces have structural Standard electrical equipment includes:. 2-100 watt spar construction with stressed skins riveted to the la"ding lights, 2-100 watt taxi lights, nawgation lights, spars and ribs. Dual control wheels accompany the interior lights,instrument panel/glareshield lights, gear conventional flight controls. The pilot’s rudder pedals and stall warning system, an electrical fuel boost have toe brakes linked to individual hydraulic cylinders pumpl an electric starter, an electric gear that supply pressure to the hydraulic disc brakes on retraction/extension system, with manual extension each main gear wheel. Removable, cc-pilot rudder override, an electric trim system (optional) and an pedals are standard equipment. The tricycle landing electrical flap system. gear, having a steerable nose wheel controlled by 5-00-05 -INSTRUMENTS rudder pedal action, is fully retractable. The wide-span trailing-edge wing flaps are electrically operated. For All flight instruments are in the shock-mounted Flight stabilizer trim, the entire empennage pivots vertically Panel. Engine instruments are in the co-pilot’s panel. about its attaching points. The pitot system provides air pressure to operate the airspeed indicator. The instrument static pressure 5-00-01 LANDING GEAR SYSTEM system has two static air pickup ports tone on each The electric landing gear system has a steerable nose side of the tailcone) that open to the atmosphere. An wheel. Single disc self-adjusting hydraulic brakes are alternate static source is provided on center console. featured on the main gear. Gear position lights, a The instrument panel/g]areshield lighting systems have warning horn and a gear position indicator on the manualdimming mechanisms. floorboard are standard equipment. Bungee springs that preload the the retraction mechanism in an 5-00-06 CABIN HEATING VENTILATING over-center position lock the gear down. An air SYSTEMS pressure actuated safety switch in the electrical system The heater muff encasing the exhaust system is the prevents electric gear retraction on takeoff until a safe cabin heat source. Hot air from the heater muff, mixed flying speed is attained. A gear throttle warning horn with ambient air, controls cabin temperature. Air routed sounds when the manifold pressure is less than a from the main heater duct system to nozzles at the pre-set value with the landing gear up. The electric windshield base defrosts the windshield. An optional gear retraction system has a manual extension system defrost blower motor system is available. connected to the gear actuator that permits manual lowering of the gear in the event of an electrical 5-00-07 FU EL SYSTEM malfunction. Landing gear doors fully enclose the The fuel system has sealed, integral wing tanks in the wheel wells to reduce sound levels and increase fonuard, inboard section of each wing. Vents at the aft, performance. outboard top corner of each tank vent through a NACA 5-00-02 FLIGHT CONTROL SYSTEMS scoop on the lower wing surface. Fuel sump drains are at the lowest point in each tank. The electn’e fuel pump The dual flight control systems can be operated from is in the bottom left forward section of the fuselage, aft either the pilot or co-pilot seat. All flight controls are of the firewall. The engine-driven fuel pump mounts on conventional in operation, using pushpull tubes to link the engine crankcase. Two fuel quantity transmitters in the control surfaces to the control wheels and rudder each tank are wired in sen’es to fuel quantity gauges in pedals. Formica guide blocks maintain control tube the engine cluster gauge. The Master Switch, left side alignment and dampen vibration. An interconnect of the pilot’s panel, activates the fuel quantity indicating spring mechanism links the aileron and rudder systems systems. The optional visual sight gauges are for to assist in control coordination. The standard co-pilot’s partial fueling of wing tanks.. rudder pedals are removable. A dual brake installation is optional for the co-pilot’s position. The manual or A 110w fuel" warning annunciator light for each tank is electric trim system sets the horizontal stabilizer angle activated when usable fuel quantity goes below 2 1/2 of attack. gallons. 5-00-03 WING FLAP SYSTEM 5-10-00 TIME LIMIT COMPONENTS Wing flaps are electrically actuated and are controlled It is recommended that overhaul or replacement of by a spring loaded "up-off-down" switch on the center components should be accomplished not later than the console. specified period of operation for that component or in accordance with manufactures service data or 5-00-04 ELECTRIC POWER SYSTEM airworthiness directives. REV. 10-98 5-00-00 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL The specified overhaul time limits, if applicable tO a NOTE component, do not constitute a guarantee that the "ON CONDITION" items are to be repaired, component will reach that time limit without requi~ng replaced or overhauled when inspection or maintenance. performance reveals an unserviceable condition. 5-1 0-01 OVERHAUL, MAINTENANCE AND REPLACEMENT SCHEDULE ITEM RECOMMENDED OVERHAUL, MAINTENANCE OR REPLACE TIME LIMITS Landing Gear Actuator No-Back Spring 1000 Hours Avionics Prddcts(Eaton) See SI M20-52A Plessey-(GEC) See SI M20-92A I All other Components On Condition Powerplant Engine 2000 Hours Propeller 2000 Hours or 6 years (refer to mfg’s. repair data) I Magnetos -iCEjl 500 Hours (refer to TCM repair/inspection data) induction Air Filter 500 Hours or Annually (recommended) All other Components On Condition Fuel IL Oil System Fuel Selector Valve (Airight or Christopher Tool) On Condition Flexible Hoses (All, except TeRon 5 as below). 7 years or Engine O/H, whichever occurs first. All other Components (in~cludes Teflon hoses) On Condition Instruments Vacuum Regulator Garter Filter 100 Hours Filters- Vacuum Pump 500 Hours (CV1J4 Filter- On Condition) Filters Gyro Instruments 500 Hours or Annually I Other Components On Condition Electrical System All Components Oni Condition Flight Controls All Components On; Condition Miscellaneous Systems Vacuum Pump, Primary. On Condition or 500 Hrs. 6 gB Engine O/H I Stand-by Vacuum Pump/Clutch 200 Hours (Insped Drive Coupling) E.L.T. Battery 2 Years or 1 Hour Total Use Oxygen Cylinders I *Lt. VI1t. Steel Cylinders 5 y;rs.(O/H)/ 24 yeaw or 10,000 recharge cycles Replace Composite C_ylinders 3 y;rs.(O/H)/ i 5 years or 10,000 recharge cycles Replace Scott Oxygen Regulator 6 years-overhaul; 3 years-test Air Conditioning Components. SeeSedion ii -5800 for specific maintenance and seNicing times. All Other Components (Excluding Avionics) On Condition (See NOTE above) Avionics Referto Manufacturers Publications Hydrostatic Test Required 3 yepr intervals. NOTE Components should be inspected and serviced at regular intervals per the servicing, lubrication and inspection chart of this manual. 5-1 0-00 REV. 10-98 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION 5-2060 -SCHEDULED MAINTENANCE 4. Pipe Threads Tightening and torque procedures. CHECKS Lubricate pipe threads as follows: Inspection Intervals. Perform a 25, 50, or 100-hour Oxygen Lines Use only MlL-T-5542 thread inspection of the aircraft, components and engine at compound or Teflon thread seal tape on threads of valves, connectors, fittings, parts or assemblies which recommended intervals as outlined in the following with oxygen. The thread might come in contact paragraphs, compound must be applied sparingly to the first three NOTE threads of the male fitting only. No compound is to be Aircraft operated in a salt air environment are used on the coupling sleeves or on the outside of the considered high risk for corrosion damage, and tube flares. Extreme care should be exercised to should be cleaned and inspected at frequent prevent the contamination of the thread compound or intervals. Refer to AC 43-4. teflon tape with oil, grease or other lubricant. Fuel, Hydraulic, Air, Oil Lines Use "Parker Thread 5-20-01 -INSPECTION CHECK POINTS Lube" or equivalent on male fittings only. Apply The general points to be covered during inspection are lubricant, omitting the first two threads, sparingly and grouped in accordance with the nature and function of carefully. the items discussed. Engine Fittings Use only aircraft engine oil to Moving Parts shall be inspected and checked as lubricate fittings threaded directly to engine. Vacuum Lines No lubn’cation is to be used. Check applicable for: proper operation, security of attachment, manufacturers instructions when installing sealing, cleanliness, lubrication, servicing, safetying, components. Refer to Section 37 for maintenance adjustment, tension, travel, condition of hinges, procedures on vacuum system. binding, excessive wear, cracking, corrosion, Tapered Threads Use Teflon Threadseal Tape. deformation, and any other apparent damage. 2. Metal Parts shall be inspected, as applicable, for: (1) Continue to tighten until fitting is correctly security of attachment, condition of finish and/or p0sitioned but do not overrun or backoff. sealant, distortion, fatigue cracks, welding cracks, (2) If leaks are detected, tighten one full tum more. corrosion, and any other apparent damage. The (3) If leaks persist, the parts should be tubular frame structure should be inspeded during disconnected and rejected; replace with new each annual inspection for any signs of corrosion or components. damage. 5. Bolts and nuts in critical areas shall be inspected 3. Fuel, air, oil and hydraulic oil lines and hoses shall for: fretting, wear, damage, stretch, proper torque, be inspected as applicable foc cracks, dents, kinks, (Figure 5-2) and safetying. deterioration, obstruction, chaffing, improper bend radius, and insecure installation. Replace or correct if 6. Electrical wiring shall be inspected as applicable any of these conditions exist. Hose clamp fO’: loose, corroded, and broken terminals; chaffed, installations on fuel and hydraulic systems between broken, and wom insulation; insecure installation; heat systems or between systems and the engine shall be deterioration; and any other apparent damage. torqued to 25 inch pounds. Hose clamp 7. Filters and screens shall be removed, cleaned and installations on blast tubes, air ducts, vacuum inspected for contamination or damage that would lines, drain and vent lines shall be torqued to 15 require replacement. inch pounds. TORQUE VALUES See Following Tables. REV. 10-98 5-20-00 Island Enterprises MOONEY AIRCRAFT CORPORATION MZOR SERVICE AND MAINTENANCE MANUAL FLARE NUT TORQUE VALUES- T~ghten to min’imum torque value for appropriate size as shown (Figure 51). CAUTION These torque values are deri)/ed from oil-free cadmium-plated threads. FITTING SIZE ALUMINUM TUBING STEEL TUBING TORQUE INCH POUNDS MINIMUM i MAXIMUM MINIMUM MAXIMUM -3 30 70 -4 4b ,j 50 90 -5 60 80 70 120 -6 75 125 90 150 -8 150 250 155 250 -10 200 i 350 300 400 -12 300 500 430 575 -16 500 700 550 750 -20 600 900 -24 600 1 900 FLAPENUTMWUE FIGURE 51 METRIC BPLTS. SCREWS 8 NUTS Failure of threaded fasteners due to over-tightening can occur by bolt shank fracture or by stripping of the nut and/or bolts thread. A bolt or screw assembled with a nut of the appropriate class is intended to provide an assem- bly capable of being tightened to the bolt proof load without thread stripping occurring. The torque value to be set for a particular size of 54rew is dependent upon: 1) Material of the screw. 2) Parent material (steel, non-ferrous metal or plastic). 3) V~hether the screw is untreated or plated. 4) V~hether the screw is dry or lubricated. 5) The depth of the thread. TIGHTENING TORQUES Untreated Hardware (Black Finish) Fiicfion Coefficienf 0. 14 NOMINAL 5.6 8.8 PROPERPI 10.9 12.9 DIAMETER CLASS (Coarre Thread) Nmlff.lb. Nmlff~lb. TORQUE Ma Nmlff.lb. Nmlff.lb. Ms 0.60/0.44 1.37/11.01 1.92/1.42 2.30/1.70 M4 1.37/1.01 3.1 0121.29 4.40/3.25 5.25/3.87 Ms 2.70/1 .99 6.15/4.54 8.65/6.38 19.4n.6 Ms 4.6/3.3 10.5/7.7 15/11 18/13 M7 7.6/5.6 17.5/112.9 25/18.4 29/21.3 Ms 1118.1 2~1B 36/26 43/31 M10 22/16 51 137 72/53 87/64 M12 39/28 89/65 125/92 150/110 M14 62/45 i 41 1~103 198/146 240/in Mis 95/70 21 5/1158 305/224 365/269 Mis 130/95 295/217 420/309 500/368 Mn 250/1 84 570/ 800/590 960/708 M20 184/135 590/435 71 0/523 M24 31 5/232 1020/752 1220/899 M27 470/346 1070/789 1510/1113 1810/1334 M30 635/468 1450/1/069 2050/1511 2450/i 806 M33 865/637 19701i452 27/0/2042 3330/2455 M36 11111819 2530/11865 3560/2625 4280/31 56 M39 1440/1062 3290/a426 4620/5407 5550/4093 5-20-01 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION (METRIC TORQUE TABILES CONTINUED) 8.8 ~PSBIY 10.9 12.9 Nm/ft.lb. Nm/ft.lb. Nm/ft.lb. TORQUE Ma MFn08xXlhS 38/28 45/33 73/53 88/64 M12 x 1.25 95/70 135/99 160/118 M14 x 1.5 150/110 210/154 M16 x 1.5 225/165 315/232 M18 x 1.5 325/239 460/339 550/405 M20 x 1.5 460/339 640/472 115 )316~dfja3;bl1 M24 x 2 TIGHTENING TORQUES Electrically Zinc Plated Hardware Friction Coefficient 8. 125 10.9 62.9 Nm/ft.lb. Nmm.lb. Nm/ft.ib. Nmm.lb. 5.6 8.8 0.56/0.41 1.28/0.94 1.80/1.33 2.15/1.59 2.90/2.14 4.10/3.02 4 Ic,rJ 5.75/4.24 8.10/5.97 Me 4.3/3.1 9.9/7.3 14/10.3 16.5/12.1 7.2!1!1/5.25 66.5/12.1 2~ij16.9 10.5/7.7 2~7 M12 36126 83/61 117/86.2 140/103 1 185/a36 220/1 62 M14 58/42 147 M20 1 390/287 550/405 660/486 M22 230/169 530/390 745/549 890/656 M30 590/435 1900/1401 2280/1681 RA33 8001590 2580/1902 3090/2278 s.e fO.D 62.9 Plm/ft.lb. Nm~t.lb. Nm/ft.lb. TORQUE Rna Ma x 1 25/18 35/25 42/30 x 1.25 140/103 x1.25 M14x1.25 235/173 M16 x 1.5 210/154 295/217 350/258 1.8 570/420 BIA241x 2 720/531 METRIC CONVERSION FACTOR: One Nm(Newton Meter~ .7375 Foot Pound; One Foot Pound 1.355818 Nna 5-2069 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL AN/MS STANDARD BOLT, NUTS TORQUE TABLES FINE-fHREAD SERIES TENSION-type SMEAR-type TENS1ON-type SMEAR -type NUT/BOLT AN()BOLTS AN()BOLTS NAS() BOLTS NAS() BOLTS SIZE AN365/AN310 AN364/AN320 AN365/AN310 AN364/AN320 NUTS NUTS NUTS NUTS 8-36 12-15 7-9 10-32 20-25 12-15 25-30 15-20 1/4-28. 50-70 30-40 80-1 00 50-60 5/16-24 100-140 60-85 120-145 70-90 3/8-24 160-190 95-110 200-250 120-150 7/16-20 450-500 270-300 520-630 300-400 1/2-20 480-690 290-410 770-950 450-550 9/16-18 800-1 000 480-600 1100-1300 650-800 5/8-18 1100-1300 600-780 1250-1550 750-950 3/4-16 2300-2500 1300-1500 2650-3200 1600-1900 7/8-14 2500-3000 1500-1800. 3550-4350 2100-2600 1-14 3700-5500 2200-3300. 4500-5500 2700-3300 11/8-12. 5000-7000 8000-4200 6000-7300 3600-4400 11/4-12 9000-11000 5400-6600 11000-13000 6600-8000 COARSE-THREAD SERIES 8-32 12-15 7-9 10-24 20-25 12-15 1/4-20. 40-50 25-30 5/1 6-18 80-90 48-55 3/8-16 160-185 95-1 00 7/16-14 235-255 140-155 1/2-13 400-480 240-290 9/16-12 500-700 300-420 518-11 700-900 420-540 314-10 1150-1600 700-959 7/8-9 2200-3000 1300-1800 TOFPQUE VALUES (Units are In$h-pounds) Figure 5-2 Reference: Federal Aviation Agency Advisory Circular No. 43.13-1A, p. 118 Recommended Torque Values for Nut-Bolt combination (Units are inch-pounds) 1. Be sure nut and/or bolt threads are clean and dry(unless Mfg, states otherwise). 2. Run bolt down near contact with washer or bearing surface and check "friction drag torque" required to turn bolt/nut. 3. Add "friction drag torque" to the recommended torque value from Figure 5-2. This value is considered "Final Torque Value". (FRICTION DRAG TORQUE i REC’MD TORQUE FINAL TORQUE). CAUTION DO NOT REUSE LOCKNUTS IF THEY CAN BE RUN UP FINGER TIGHT. 5-20-01 REV. 10-98 10 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONP/ AIRCRAFT CORPORATION 8-20-02 -AIRCRAFT FILE INSPECTION inspection doors, panels, or fairings. After the first 25 Aircraft 100-hour and annual inspections cover, in hours of operating time, a new, re-manufactured, or addition to examining the aircraft proper, a review of newly overhauled engine should be given a 50-hour the status of compliance with current Federal Aviation including replacement of the lubricating oil Regulations. This review includes inspection of the Airplane Flight Manual, Aircraft Log Book, Engine Log 1. Engine Inspections. (Refer to engine Book, Propeller Log Book, Registration Certificate, manufacturer’s service data for oil change frequency) Airworthiness Certificate, Weight 5 Balance Record, A. Drain engine oil sump. Engine Service Information, Aircraft Radio Station B. Remove and clean suction oil strainer; reinstall License (if applicable), FAA Airworthiness Directives, strainer and plug. Safety wire strainer plug. and Mooney service documents. C. Remove and replace the full-flow oil filter cartridge. 5-201)3 ENGINE FUNCTIONAL CHECK D. Remove and clean fuel injector fuel strainer. Prior to a scheduled 100-hour or annual inspedion, E. Service engine oil sump with proper type, grade, and/or 25 hours after installation of new or overhauled a"d amount of lubricating oil. engine, wash down the engine and engine components. F. Inspect engine intake and exhaust systems for Then perform an engine runup in accord with procedure evidence of leakage, looseness or damage. recommended in the Airplane Flight Manual. Make a G. inspect spark plug elbows and shielding nuts for record of all malfunctions and abnormalities. After the security. engine runup, comdete a differential (hot engine) H. Inspect cylinders for evidence of ovemeating. compression check. to verify conedion of malfunctions Engine Installation inspections. and abnormalities, perform a second engine runup and a I. inspect baffles for secure anchorage, close fit Right test after completing the inspection. around cylinders, and Freedom from cracks. J. Inspect engine controls for full travel, freedom of 530-04 FIRST 25-HOURS INSPECTION movement, and security. (Non-Repetitive) K. Drain and clean fuel strainer (Gascolator) I The, one time, 25-hour inspection consists of a visual L. Visually inspect fuel and oil lines for security of inspedion of the propeller, engine, and aircraft general connections and evidence of leakage or damage. condition, including a preflight inspection as outlined in M. Wsually inspect induction air system; check the Airplane Flight Manual. The inspection does not opention of alternate-air door (refer to paragraph require removal of all access panels or disassembly of 71-62-00). components; however, 1 should include completion of N. Inspect engine mount bolts firewall 5 Lord all lubrication 8 service requirements. The inspection isolator mounts for security and condition. should be extensive enough to detect any damage or 2. Propeller. maladjustment which might jeopardize Right safety. A. Inspect propeller hub and spinner for general After the Zrst 25 hours of a new or ovemauled engine condition, looseness, and/or oil leakage. operation, refer to paragraph 5-20-05 for the B. Inspect blades for nicks and cmcks. Repair any recommended engine inspection. discrepancy prior to ne~d Right 1. Visually inspect propeller, spinner, and engine 3. Cabin. cowling; remove cowling. A. Inspect brake and parking brake control 2. Inspect and clean induction air filter a aircraff has systems for proper operation and fluid level. been operating under dusty conditions. Check B. inspect trim system and indicator for free operation of alternate air door. operation and travel. 3. inspect engine compartment for evidence of fuel, C. Inspect cabin and baggage doors for damage, proper operation, and sealing. oil or exhaust leaks. D. Lights Inspect cabin interior, instrument panel, 4. Inspect security and condition of equipment position,antLcollision and landing and taxi installed on engine. 5. Insped fuselage, wing and empennage for "E: Inspect fuel selector valve, gascolator, and extemal evidence of damage. Pay particular attention boost pump for proper operation. to scratches and dents. F. Inspect oxygen system, plumbing and 6. Inspect windshields and windows for crazing, attachments (ifinstalled). cracks, and scratches. 7. Inspect control systems for binding, excessive 4. Landing Gear. freeplay, and damage. tires for cuts, blisters, wear and proper 8. Inspect pitot and static systems for possible B. Inspect shock discs for proper e>dension at obstructions. aircraft static weight. 9. Inspect aircraft e>derior for security of bolts, C. inspect hydraulic brake system for disc or pad screws, etc. wear, disc warpage, hydraulic fluid level and proper 10. Inspect and service batteries. installation. 5. ~Hngs. 5-20QI 80+10UR INSPECTIOPI -(Repetitive) A. inspect surfaces and tips for damage. The S0-hour inspection includes all requirements of the B. Inspect ailerons, aileron attachments, and 25-hour inspection, plus the necessary removal of bellcranks for damage and proper operation. REV. 10-98 5-20-02 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL C. Inspect flaps and attachments for damage ~nd exhaust/manifold connections and engine exhaust proper operation. Cycle flaps, observe travel and ~ny manifolds (SEE Pare. 5-20-06, Q, R S below). evidence of binding. H. Remove and clean induction air filter (replace at D. Lubricate contrds per Section 5´•20-07, if necess~iry. 500 Hrs). Inspect altemate air door and magnet for 6. Fuselage and Empennage. security and operation. Inspect all air ducting and A. Inspect stabilizer, elevators, fin, and Ndde~ for connections in the induction air system for leaks. damage, proper operation and proper attachment. i. check magnetos for grounding and a. Lubricate controls per section ~20´•07, if necessery. Sy"ch""ization (timing to engine); inspect magneto C. Check Trim System for proper operation, points for condition, clearance, and intemai timing. Inspect distributor block for erosion and cracks. Inspect 7. See Section 5-20-07 for any repetitive 50 tiour cam follower felt for proper lubrication, and remove inspections and component service guides, excessive oil from breaker compartment. At 500 hours inspect magneto per TCM/magneto maintenance 5-20-06 100-HOUR INSPECTION for manual. Repair or replace components, if required. ANNUAL INSPECTIONS) J. Inspect baffles for secure anchorage, cracks, (Refer to Pig. 53) holes, deformation, and for dose frt around cylinders. Inspect cylinders for bumed paint and cracked and The 100-hour (or annual) inspection is a broken fins. Inspect baffle sealant. searching inspection of the entire aircraft, starter, altemator, I for the inspedion includes the thorough of K. Insped accessory case, AIC e~cterior, engine and engine compartment, vacuum pumps hoses, firewall and fittings for security of all fuselage, wing, and empennage inspection and damage. cover plates, and fairings at all systems attach, L. inspect tubular engine mount for cracks, and bearing locations (including wing and damage and corrosion; inspect all bolts and rubber to fuselage mating points). Operating isolation mounts for security and condition. M. Inspect engine and pmpeller co~ds for free replacements (See Section 5-10-01) and Directives, Airworthinessess biieclives Notes (AD’s), attachment testing of components is to be included at this i operation, full travel, proper connection (security) of cable when applicable. Comply with applicable AA housing swage at the HEAD tube and security of applicable Mooney or Vendor mandatory NOTE Bulletins and Instructions. Check for conformance to FAA Specification 2A3 for Cablecraft control cables are lubricated for the life of the central cable. DO NOT REMOVE seals Model aircraft. or lubricate control cable. Recommended 100-hour/annual and special inspe~ion requirements are outlined in the following paragraphs: N. Inspect propeller govemor for evidence of leakage and mounting security. anengine runup in accord with 100 hour 71-00-50. i. ENGINE INSPECTION. Prior to the i remove engine cowling and propeller spinner. O. Inspect engine for proper set-up. (566 TCM engine and engine compartment down. Then Service information for IO-550-G engine and Section recommended in TCM Engine Maintenance P. Inspect battery cables, electrical wiring, and Operators Manual. To verify corection of malfun ignition harness for condition, secure anchorage, loose and abnormalities, perform a second runup and terminals, and bumed or chaffed insulation. test after the 100-hour/annual inspedion engine set-~p. Q. Inspect batteries, battery mount areas, and vent A. Complete a differential (hot engine) compres$ion system for condition and corrosion. Inspect blast tube check (Ref. TCM SE M84-15 or current rev.): clean ~nd for obstrction. Flush battery mount areas with soda gap or ~place spark plugs, if necessary. solution to neutralize conosive action, if necessary. B. Inspect engine for evidence of fuel andi oil R. Inspect exhaust system for cracks, looseness leakage. Inspect oil cooler. Inspect oil and fuel hoises and for evidence of leakage. Replace or repair for condition and security, damaged area. Replace or repair muffler if any internal clean oil suction screens; reinstall andsafety.C. Drain engine oil sump; remove, damage is found. full-flow oil filter cartridge; replace with new S. Inspect exhaust stacks for bumed areas, cracks, distortion and looseness. and safety. It is recommended that old filter be opehed T. Inspect airconditioning compressor installation, up to check for metal particles 8 foreign matter. Check belts,connections (if installed). Reference SECTION crank case breather lines for obstruction. Safety ivire 21-58-00. oil filter installation. U. Inspect studs, nuts, bolts, etc. For damage and D. Refill engine oil sump with the proper t~pe, propertorque. grade, and quantity of lubricating oil. V. Inspect exhaust couplings, seals, clamps and E. Inspect fuel injedor, fuel line connedionsjfor slipjoints for cracks, deformation, leaks and security. security and condition and fuel naules (Ref TCM SE). W. Inspect and re-install cowling. F. Remove and inspect gascolator strainer, rein~tall strainer. Inspect fuel lines arid connections: pres$ure 2´• PROPELLER INSPECTION. check fuel system with mi>dure control at IDLE CUTOFF A. Remove spinner (if not already removed). and BOOST PUMP ’ON". B. Inspect security of propeller installation. G. Inspect all air ducting and connections in c~bin C. Inspect hub studs/nuts/bolts for proper torque Iheating air systems for leaks. Leak check all (ref. 81-00-20,5,6), security and damage. 5-20-06 :REV. 10-98 12 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONC( AIRCRAFT CORPORATION D. Inspect hub components for damage and leaks, E. inspect fuel selector valve for proper tank and blades for cracks and nicks. Repair prior to ne~d selection, smooth operation and any leakage when in flight. OFF position. E. Inspect Anti-ice boots for security or damage in F. Inspect gascolator for leakage; inspect sump for accordance with MoCauley Manual No. 830415, Section 4. sediment, water and other contamination. F. Inspect spinner and bulkhead kx cracks and condSon. G. Inspect electric boost pump for leaks, security of G. Inspect spinner bulkhead for snug fit be~ween mounting, adequate fuel pressure, switch operation, propeller hub cylinder and rear bulkhead. Use shims as and condition of wiring and electrical connections. necessary for snug fit. (1) Check electric boost pump for proper operation by ’T ing" into line with a calibrated fuel pressure gauge. 3. LANDING GEAR and RETRACTION SYSTEM High boost operation should result in a 15 P.S.I. INSPECTION. reading (mWure full RICH, throttle-IDLE). A. Inspect tires for proper inflation, cuts, blisters, H. Inspect fuel quantity gauges and transmitters for slippage and excessive wear. Replace with new, security of mounting and condition of wiring and approved, tire(s), a necessary, electrical connections. CAUTION I. inspect fuel tank filler port for cleanliness, cap Always run at least 5 complete Landing Gear security, and condition of servicing placards. Inspect Retraction Cycle checks after any tire has been fuel filler cap O’rings for condition and replace if removed andlor rePlaced, before flying the needed (Reference Section 2&00-01). aircraft. 5. EXTERIOR INSPECTION. A. inspect fuselage exterior surfaces for corrosion, B. Inspect wheels for cracks, distortion, damage, loose and popped rivets, dents, misalignment, corrosion and bolt failure. Inspect oilcans(stretched skins), scratches, cracks and condition of felt seals and bearings; re-pack bearings deteriorated paint. at 250 hour intervals. B. Inspect windshields and windows for cracks, crazing, C. inspect brakes for disc and pad wear, and disc scratches, condition of seahnt, and security of installation. warpage (Ref. Section 32-40-04). C. inspect wings, flaps, and ailerons for corrosion, D. inspect hydraulic reservoir for proper fluid level. damage, loose or popped rivets, dents, scratches, E. inspect hydraulic brake lines and hoses for cracks, condition of attaching points, lubrication, leakage, dents, cracks chafing, kinks and security, freedom of operation, free-play, travel, and balance F. Inspect parking brake system for proper weight attachment. engagement and release. D. If installed, inspect Airframe De-ice CTKS) G. Check shock disc gap on main and nose components for damage, leakage operation per landing gear leg assemblies. (Ref. 32-81-00) SECTION 30-12-00 through 30-12-02. E. Inspect Speed Brake cartridges for damage or Jack aircraft, as recommended in paragraph 7-10-00, wear. Check for proper operation. (Ref. 27-96-01) for the following inspections: F. inspect empennage for corrosion, damage, H. Hard landing inspedion (ref. 32-82-00) loose or popped nvets, free-play, dents, scratches, I. Inspect nose gear for cleanliness and damage. cracks, condition and lubrication of hinge points, Insped nose gear re~raction tube bungees for sheared attachment of balance weights and freedom of or broken roll pins, operation, manually and electrically. G. inspect cabin door and door: frames for damage, NOTE corrosion, nicks, dents, hinge secuiity and lubrication. Maximum allowable towlngdamage;on leg H. inspect cabin door lock mechanism for :assembiy is 1/32 inch dent. No repair is allowed .lubrication- and proper engagement. See’Section on heat trea~ted landing gear components. .52-11-00forrigging procedures. J. Inspect nose wheel steering mechanism for :L´• Inspect baggage door and baggage adjustment, a’lignment, c~rrosioil,‘and lubrication. compartment for damage, corrosion, warpage, hinge K. Inspect main gear for cleanliness and damage. security, condition to door frame and door seals, condition and operation of door locking mechanism L. Inspect landing gear retraction linkage, bellcranks, ,,d condition of cargo restraintsniedowns. pivots and bearings for wear, damage, distortion, J. inspect ventilating system drain line for obstruction. misalignment, corrosion, cleanliness, and lubrication. K. Inspect landing and ta~d lights for security, M. Inspect landing gear actuator for security of condition and proper adjustment. See Section mounting, cleanliness, and indication of overheating 33-43-00 for adjustment procedures. and damage. Check motor operation and brush wear. L. Inspect e~temal Decals/Placards for security. N. Perform landing gear operational check per M. Lightning Strike Inspection, e~derior/interior.. Section 32-30-01. 6. lNTERIOR INSPECTION. 4. FUEL SYSTEM INSPECTION. A. Inspect seats, seat tracks, and upholstery for A. Inspect fuel tank exterior for evidence of fuel cleanliness and mounting security. Inspect seats for seepage and stain. condition and operation of position locks. Inspect seat B. Drain tank and inspect tank interior when structure for cracks, deformation, corrosion and seepage is evident. mechanism lubrication. C. Inspect fuel tank drains for leakage, sediment, B. hsped safety bets, harness and attaching brad<ets for and water contamination. deanCness, oondilicn latch operation and seculaj of D. inspect fuel-tank vents for obstruction. attachment REV. 10-98 5-20-06 13 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL C. Inspect for loose equipment, etc, that n~igM F. Check flap system for rigging actuator, push/pull restrict control movements. tubes for rigging, travel, and stop adjustment. Check D. Inspect Oxygen system (if installed) per CHAP~ER flap posnion indicator for proper operation. Inspect 35 of this S M manual. actuator, push-pull tubes, flap rods, interconnects, I E. Inspect interior Decals/Placards for security, bellcranks and hinges for corrosion, security, and 7. INTERNAL INSPECTION. A. Open inspection doors and remove acCess NOTE panels and fairings as required. All control rigging inspections should be made B. Inspect wing attaching bolts for proper tot~ue with the aircraftjacked and leveled (Per Section and safetying, and evidence of damage and corro/sion 7) and landing gear retracted. (interior ABS side panels/carpet will require remov’al to adequately accomplish this inspection). NOTE C. Inspect forward side of firewall for damage. Some elevator trim tubes have poly tape D. Inspect tubular structure for corrosioniand wrapped at bulkhead penetrations. lftape damage (interior side panels will require remo~val), shows; signs of wear, re-wrap tube with 2" wide I (Reference Mooney Service Bulletin M20-208Ai for V9265 polyurethane tape (1/2 tape overlap). specific procedures required annually). Trim tubes, without tape, which show signs of E. inspect wing ribs and stringers for cracksiand abrading bulkhead grommet should be evidence of damage and corrosion. wrapped. See SE M20-185. F. Inspect wing spars for damage, distortion, cracks, and corrosion. MAX. TUBE V\fiAR-.00’1 in. wall thickness or.014 in. G. Inspect electrical wiring, fuel, oil and hydraulic diameter reduction. lines and air ducts for security, damage, interferehce 9. INSTRUMENTIAVIONICS INSPECTION. chaffing and de-bonding. A. Inspect all instrument wiring and plumbing for Icondition and proper connections. NOTE B. Clean and inspect vacuum finer. Replace garter Seal ah receptacles and plugs outside cabir) filter on vacuum regulator. environment with Dow Coming #4. C. Inspect vacuum regulator at vacuum manifold. H. inspect wing interior for foreign mat$rial, Check operation of high-and low-vacuum warning corrosion, and evidence of fuel leakage. lights or vacuum gage. Inspect Stand-by Vacuum I. Inspect empennage attachment brackets ´•and System (Ref. Section 37-40-00) hardware for corrosion. D. Inspect all instruments for proper pointer 8. FLIGHT CONTROL INSPECTION. indication, range and limit markings, condition of A. Inspect control column and control wheels for full indicator markings, cracked or loose glass, slippage or marks, and security of installation. trael, proper rigging, fre~play, binding, fOF proper lighting, mounting, proper lubrication and proper direction of E. Inspect compass surface movement wW relation to control compensation, security of mounting, liquid leakage and movement. discoloration. Swing compass at annual inspection and after any new equipment has been installed. CAUTION Degaussing tubular strudure may be necessary if All flight control components should be _ compass will not compensate within 100. See Mooney inspected to verify that ad moisture drain holds Service Instruction M20-95. are free of obstructions. F. Inspect alimeter for scale error, discolored B. Inspect elevator system for damage, markings, proper pointer readings, setting knob lubrication, rigging, travel, stop adjustment, ,,,u,.,y,, Oi freedom and synchronization of barometric scale with reference markers. all bearings, pivots, bellcranks, hinges wear on G. Inspect flight panel for security of mounting, downspring eyes, cable pulley and finings, security of mounting and proper relation to control movement.; condition of shock mounts, freedom from interference with structure and condition of ground straps. C. Inspect aileron system for damage, corro$ion, H. Insped Avionics Equipment for proper operation lubrication, rigging, travel, stop adjustment, conditi(ln of 8 security. hinges, bellcranks, pivots and rod end bearings,llink I. Inspect Avionics Antennas, wiring, shielding for bolt security and proper relation to control movemeClt. D. Inspect rudder system for damage, corro$ion, ObViOUS damage or defects. lubrication, rigging, condition of hinges, bellcra:nks, J. Inspect pitot head for port obstruction; inspect lines pivots and rod-end bearings, link bolt security iand for cracks, dents, kinks, proper bend radius and security of proper relation to control movement. Check for ifree Bttachment. Drain system and insped for leaks. movement of toe-brake pedals and proper rudderiand K´• I"sped static ports for obstruction and nose wheel travel. aerodynamic smoothness at port installations. Inspect E. inspect stabilizer trim control system for secClrity lines for bends, cracks, dents, kinks, and security of and proper adjustment, shaft and stop nuts forf,, pt~0per 8ttachment. Drain system and inspect for leaks. Check rigging trim control wheel for smooth operation, altemate static pressure source located on flight panel unlve~al joints for free-play and good working older, fo’ freedom of valve movement. actuator threads for lubrication, linkage for conogion, io. ELECTRICAL FUNCTIONAL TEST. and guide blocks for looseness or excessive wear. ISee A. Check operation of navigation lights. SECTION 27-42-00 for Electric Trim System be~ring B. Check operation of landing 8 taxi lights. maintenance. C. Check operation of dome lights and cigar lighter. 520-06 i REV. 10-98 14 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION D. Check operation of anticollision lights. M. Check operation of’Prop De-ice" (if installed). E. Check operation of instrument and placard Push switch ’ON", observe prop de-ice annunciator for lights. Check rheostat travel for dimming without any illumination (BLUE light). Observe ammeter for dropouts. fluctuation during cycle action oftimer. F. Check ope~ation of pitot head heater (short N. Inspect batteries, connection 8 battery areas for duration only) by observing ammeter needle flucuation. proper k~stalletion corrosion and cleanliness. G. Check operation of cluster gauge. ii. MISCEU4NEOUS/OPTIONAL EQUIPMENT H. Check operation of fuel gauges. A. Inspect any other installed equipment not I. Check operation of annunciator light press-to-test covered by previous paragraphs for proper operation, switch. attachment and obvious damage or malfunctions. J. Check operation of ignition switch, and starter 12~ POST INSPECTION FLIGHT TEST. solenoid. K. Check operation of landing gear position lights Flight test the aircraft to verify correction of all (See Section 24-36-00 8 3260-00) and warning hom malfunctions and abnormalities. Make proper entries in (See Section 32-00-00). aircraft log book. L. During post inspection flight, check proper Wing access covers may vary to some degree setting/operation of stall warning hem. between model year aircraft. Component locations remain basically unchanged. REFERENCE FIGURE 5-3 FOR LOCATION OF THE FOLLOWING COMPONENTS NOTE Access covers riveted in place during production need not be removed for routine inspections. 5-20-01 -ACCESS COVER IDENTIFICATION, LUBRICATION AND SERVICE GUIDE ITEM ITEM DESCRIPTION LUBRICATION INTERVAL Number. SYMBOL’ (HRS) 1 Flight Instruments Vacuum Regulator Turn Coordinator Vacuum Filters--Replace at m 500 Control System Adjustments: Control Column Bearing Ball ~1 100 Rod End Bearings. yl 100 Universal Joints I: 100 BellcranksC 100 I Engine Cowling Q 100 *CI~ 500 Vacuum Pumps Q. See last page of section for lubrication symbol legend. No periodicSubricant on Avionics Products #102000-2. If necessary to relubricate, use Aeroshell 22, Mobil 28 or MlL-G-81322 ONLY. Change garter filter on vacuum regulator every 100 hours. Change instrument filters at 500 hours, clean every 100 hours. inspect Stand-by Vacuum Pump drive coupling every 200 hours. (Refer to Airbome Service Letter No. 34) ITEM ITEM DESCRIPTION LUBRICATION INTERVAL No. SYMBOL" (HRS) 3 Nose Gear Grease Fittings R 100 Retraction Tube Rod End Bearings W 100 Bellcranks. C 100 Bungees \Y 100 Gear Door Rod End Bearings. y, 50 4 Main Gear Grease Fittings R 100 Retraction Tube Rod End Bearings W 100 Bellcranks. C 100 Bungees C 100 Gear Door Rod End Bearings. yr 50 Electric Gear Actuator Gear Box" R AR Electric Gear Actuator Ball Screw. i 000 REV. 10-98 5-20-07 15 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL FIGURE 5-3 ACCESS COVER IDENTIFICAflON, LUBRICATION SERVICE GUIDE 23 7 1 IC~n L ~n \’9 7 L 8 2~ L3 L4 L5 29 18 13 13 30 28 31 10 10 11 12 12 14 14 12 12 11 32 I’ I~LI ’I I I I I r 32 c>o c~ o o o,,, C) O 0 0 ,ooo o 00 000 0 000 00 o o 27 27 27 27 19 17 15 16 19 o o cp o 27 27 27 20 r 21 22 7 14-----_L/ I 26 25 33 24 (@rr SMR5-3 5-20-07 16 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION ITEM ITEM DESCRIPTION LUBRICATION INTERVAL No. SYMBOL" (HRS) 5 Elevator 8 Rudder Controls: Control Tube Rod End Bearings y, 100 Bellcranks C 100 Batteries Stabilizer Trim Control Shaft: Universal Joints C 100 Guide Blocks 100 Hydraulic Reservoir P 50 Oxygen, High PressureFittins; .A........... 50 6 Elevator 8 Rudder Controls: Control Tube Rod End Bearings yl 100 Bellcranks C 100 Stabilizer Trim Jack Screw/Actuator Brgs. .O 100 Variable Downspring System W 100 Tail Strobe Light Power Supply Q 100 7 Empennage Attach Points. Q 100 Sta bilizer Trim Attach Point Q 1 00 8 Elevator Rudder controls: Control Tube Rod End Bearings W 100 9 Elevator 8 Rudder Controls: Control Tube Rod End Bearings \V 100 10 Aileron Control Tube Guide Blocks 100 11 Aileron Controls: Control Tube Rod End Bearings y, 100 Bellcranks C 100 12 Aileron Control Tube Guide Blocks 100 13 Main Gear Retraction C 100 14 Wing Points i~ 100 Control Tube Guide Blocks 100 15 Stabilizer Trim Screw Stops. 0 100 Indicator Adjustment Point Stabilizer Trim Chain Gear 100 16 Elevator Rudder Controls: Control Tube Rod End Bearings \y 100 Bellcranks C 100 GuideBlocks 100 Flap IndicatorCable C 100 Electric Flap Actuator Gear Box R 500 Electric Flap Actuator Ball Screw B 100 17 Electric Boost Pump Gascolator. C 50 18 Control Systems: Control Tube Rod End Bearings \y 100 Control Yoke (Lower Section) C 100 NLGr Steering Link Rod End Brgs y, 100 Rudder Pedal Cross Shaft C 100 REV. 10-98 5-20-07 17 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL ITEM ITEM DESCRIPTION LUBRICATION INTERVAL No. SYMBOL" (HRS) Rudder-Aileron Bungee C 100 Hyd. Brake Cylinder Pedal Linkage C 100 19 Aileron Control Tube Rod End Brgs y, 100 Outboard Flap Stops 0. 20 Baggage Compartment Door: Hinges C 100 Latches 100 Lock. ii 100 Seals Z! 100 Hold Open arm 100 2rli Cabin Door: Hinges I. C 100 Latches C 100 Lock. 6 100 Seals 100 Hold-Open Arm 100 22 Engine Instruments Radios Engine Controls yl 100 23 Oil Dip Stick, Oil Filler Tube V AR 24 Wheels 8 Brakes: Wheel Bearings 250 Brake Pressure Plates Anchor Bolts y, 50 8 Guide Pins Shock Discs. a 50 25 Elevator 8 Rudder Control Stops 100 26 Nose Wheel: Wheel Bearings 250 Shock Discs. 0 50 27 Control Surface Hinges C 100 28 Exhaust Assy 0 100 28 Air Induction Filter. 0 100 30 Cabin Heat Shroud Ducts O 100 31 Remote Compass Flux Valve 0 100 32 Strobelight Power Supply O~ng) 0 100 I" ELT (Batteries) Q 100 Stand-by Vacuum Pump System O 100 34 ELT ANTENNA (UNDER DORSAL PIN) AR 5-20-07 REV. 10-98 18 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION LUBRICATION SYMBOL LEGEND SYMBOL MIL. SPEC. NO. DESCRIPTION C MIL-L-7870 Low Temperature Oil (General Purpose) SZ MIL-G-81322 Grease y, MIL-L-3545 Grease (High Temperature) P MIL-H-5606 Hydraulic Fluid (Red) Graphite M1L-G-3278 Grease or MIL-G-23827 8 Powdered Graphite ~Y Teflon Spray CTri-Flow) or Equivalent G´• Stick Lubricant (Door Ease or Equivalent) 0 Aeroshell Grease NO. 7 (On jackscrew and inside Actuator Bearing Housing) Lubriplate 630AA (10% by Volume Molybdenum Disulfide Mixture Permissible) 6 Seal Dressing C1 Inspect ii Tape, Tetrafluoroethylene (M1L-T-27730) Permacel Tape Corp., New Brunswick, NJ V TCM Spec. MHS-24( Viscosity Requirements Above 30 Deg F Ambient, S.L. SAE 40 or SAE 15W-50 Below 30 Deg F Ambient, S.L. SAE 30 or SAE 20W-30 NOTE Mooney Aircraft are delivered with the proper break-in oil; MIL-C-6529, Type II. This oil should be changed, after 25 hours or after oil consumption has stabilized, to oil conforming to TCM Specification MHS-24( For M20R aircraft S/N 29-0001 ON It is recommended to use multiviscosity oil in these aircraft, both mineral 8 additive oil. REV. 10-98 5-20-07 19 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL BLANK 5-20-07 20 Island Enterprises CHAPTER DIMENSIONS AND AREAS Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 6 DIMENSIONS AND AREAS LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT .PAGE DATE 6-Eff/Contents 1/2BLANK 5-94 6-00-00 3 5-94 6-00-02 4 5-94 6-00-03 5 5-94 6-00-03 6 5-94 6-00-03 7 5-94 6-00-03 8 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 6-00-00 Dimensions and Areas .3 6-00-01 Aircraft Specifications .3 6-00-02 Aircraft Dimensions .4 6-00-03 Aircraft Stations .5 6-EFF/CONTENTS 1/2BLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 6-00-00 DIMENSIONS AND AREAS 800-01 AIRCRAFT SPECIFICATIONS SUBJECT STANDARD METRIC/QPT/MISC. ENGINE Engine Manufacturer Teledyne Continental Motors Engine Model 1O-55o-G(5) No. Cylinders 6 Rated Horsepower 280 HP RPM 2500 Min. Fuel Octane 100 or 100 LL. Fuel Capacity Total 95 U.S. Gal. 359.6 Liters Useable 89 U.S. Gal. 336.9 Liters Oil Specification TCM Specification MHS-24( Oil Grade-Normal Service 15W50 or 20W50 Above 300 F(-10_ C)Ambient air SL SAE 50 Below 500 F(10 C)Ambient air SL SAE 30 Oil Capacity 8 qts. 7.57 Liters Minimum for Flight Oil Level 4.5 qts. 4.54 Liters First 25 hours of operation mineral (non-detergent) oil or equivalent corresponding to TCM Spec. MHS-24( Oil Pressure Idle, Minimum- 10 PSI Normal Operation so-so FdSI Max. Allowable (cold oil) 100 PSI Oil Temperature Max. Allowable 2400F 1150C Recommended Takeoff-Min 1000F 380C Recommended Flight Operation (Cruise) 170 2000F 76.6 930C Cylinder Head Temperature (CHT) Max. Allowable 4600 F 2370 C Recommended Cruise 170 to 2200 F 77 to 104" C PROPELLER Propeller Nifg. McCauley Type Constant Speed Model 3A32C41 8/G-82NRC-9 Pitch Anclle 31! in. Sta. bOW 16.10 (+/-)0.20. HIGt-1 400 (-t´•-/-)0.5" Diameter 73.0 Inches (185.4 cm) Governor McCauley (Optional Propeller N/A at this time Type Model Pitch Angla ~130 in. Sta. $OW HlGH Diametei 6-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION AIRFRAME STANDARD METRIC/OPT/MISC WEIGHTS LOADINGS: A. Approximate Empty Weight 2200 Ib. (998 Kg.) B. Gross Weight 3368 Ib. (1528 Kg.) C. Average Useful Load 1168 Ib. (529.8 Kg.) D. Wing Loading 19.26 Lbs.lSq.Ft. (94 Kg.lsq.m) E. Power Loading 12.47 Ib/hp (5.66 Kg/hp) WINGS: A. Airfoil At Wing Root 632215 B. Airfoil At Wing Tip 64~412 C. Mean Aerodynamic Chord At Wing Sta.94.8~5 61 in. 241 cm D. Center-of-Gravity Range 41.0 to 51.0 E. Geometric Twist (DEG) 1.5 Degrees F. Incidence Angle (DEG) From Sta 20. to Wing Tip 2.5 Degrees G. Dihedral angle (DEG) 5.5 Degrees H. Aspect Ratio 7.448 i. Taper Ratio (CS/CT) 2.271 FUSELAGE: A. Cabin Dimensions: (1) Height 44.5" 113 cm (2) Width 43.5" 110.5 cm (3) Length 126" 315 cm (4) Cabin Door Width 29" 73.4 cm (5) Cabin Door Height 35" 88.9 cm B. Baggage Campartment: (1) MAX.Loading 120 Ibs 54.4 kg (2) Baggage Space 22.6 Cu. Ft. 0.678 Cu. M. (3) Baggage Door Width 17" 43.2 cm (4) Baggage Door Height 20.5" 52.1 cm (5) Hat Rack Capacity 10 Ibs 4.5 kg C. Landing Gear: (1) Type Tricycle, Retractable (2) Operation Electrical (3) Wheel Track 9’ 2" 279.4 cm (4) Wheel Base 6’7 9/16" 202.08 cm (5) Tire Size- Nose (6-Ply Rating) 5.00x5 (6) Tire Size- Main (6-Ply Rating) 6.00x6 (7) Tire Pressure Nose i 49 Ibs/sq. in. (8) Tire Pressure Main 42 Ibs/sq. in. 6-00-02 AIRCRAFT DIMENSIONS DIMENSIONS: A. Wing Span 36’1" 10.998 meters B. Fuselage Length 26’9" 8.153 meters C. Tail Height 8’4" 2.54 meters D. Stabilizer Span 11’9" 3.581 meters AREAS: A. Wing 174.786 so. ft. 16.24 so. meters B. Ailerons 11.4 so. ft. 1.06 so. meters C. Flaps 17.9 so. ft. 1.66 so. meters D. Vertical Fin 7.8 so. ft. 0.73 so. meters E. Rudder 6.25 so. ft. 0.52 so. meters F. Horizontal Stabilizer 21.42 so. ft. 1.90 so. meters G. Elevators 13.0 so. ft. 1.21 so. meters 6-00-02 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 6-00-03 AIRCRAFT STATIONS NOTE The datum line station 0.0 is 13 inches aft of the nose gear trunnion pivot point. (Reference Figure 8-2.) (815.3 73’ (254 cm) (185.4 cm) C3 k-h.-7 q/l6.~srl (27.9 cm) (202,08 cm) I 35R.! cn) i. a_ 9´• -----I (’/9.´•1 cn) PRINCIPAL AIRCRAFT DIMENSIONS FIGURE 6-1 6-00-03 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION STA STA STA STA STA ;210,97 147,75 103,50 59,~5 ~4,50 STA 193,50 WING STATION RIBS FIGURE 6-iZ FIGURE 6-2 STA -5,375 STA 3,68 r_) STA STA STA STA STA STB STA 211,50 176,00 142,00 100,00 53,00 ~1,80 -5,00 FUSELAGE STATIONS SMLMR6-3 FIGURE 6-3 g-OQ-03 Island Enterprises MOQMEY AIRCRAFT CORPORATION M20R SERVICE 819D MAINTENANCE MANUAL STA STA STA STA STA 67,75 4E1,~5 4,43 70,0 STA 5;1,5Q STA ;I~5,75 STA 51~5 EMPEI\II\JAGE STATIO~IS SM6-4 EMPENNAGE STATIONS FIGURE 6-4 6-00-83 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION BLANK 0-00-00 Island Enterprises CHAPTER LIFTING AND SHORING Island Enterprises SERVICE AND MAINTENANCE MANUAL MZOR MOONEY AIRCRAFT CORPORATION CHAPTER7 LIFTING AND SHORING LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT PAGE DATE 7-Effectivity/Contents 1/2BLANK 11-95 7-1 0-00 3 1195 7-1 0-00 4 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 7-1 0-00 Jacking 3 7-EFF!CONTENTS 1/2BLANK REV.11-95 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 7-10-00 JACKING 4. Secure safety locks on each jack. When it is necessary to raise the aircraft off the ground: CAUTION When lowering aircraft on lacks bleed off pressure CAUTION on all jacks a~d evenly to keep Do not raise the aircraft on jacks, out of doors, aircraft level as it is being lowered. when wind velocity is over 16 MPH. Jacks should be on hard surface. CAUTION Individual wheels may be raised without raising 1. Install wing jack points (2) in tiedown mounting entire aircraft. Wheelsnot being raised should 6e holes outboard of each main landing gear. Install Nose checked fore and aft. Landing Gear jack point (1) (threaded, longshaff jack- NOTE point) into threaded receptacle at FUS. STA. -5.51. It is not recommended to use tail-tie down fitting 2. Use standard aircraft jacks at both wing hoist points during jacking process to lift nose wheel off (wing tiedown eyebolt receptacles) outboard of the main ground. landig gears and at the nose landing gear (extended shaft) jack point. V~hile holding wing jack points in place, CAUTION j raise jack to firmly contact jack point. Nose landing gear Do not leave aircraft on jacks for extended periods jack point is located under the cowling at Fuselage Sta- while a tailstand is in place. The wing jack(i)_may bleed down and put excessive loads on the front tion -5.51. jack point and tailcone. 3. Raise aircraft, keeping wings as nearly level as pos- sible. REV.11-95 7-1 0-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOQNEY AIRCRAFT CORPORATION BLAN~ 7-10-00 Island Enterprises C H A PT E R LEVELING AND ~N EIGHING Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 8 LEVELING AND WEIGHING LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT PAGE DATE 8-Effectivity/Contents 1/2BLANK 10-98 8-00-00 3 10-98 88-00-01. 4 10-98 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 8-00-00 Leveling 8-00-01 Weight and Balance 3 REV. 10-98 8-EFF/CONTENTS 1RBLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 8-00-00 -LEVELING 10-02, 2. Place a spirit level on the leveling screws above the tail- 4. Add unusable fuel to each tank, (5ee Pilot’s Oper- cone access door when leveling the aircraft longitudi- ating Handbook for proper quantity of unusable fuel). nally. Level the aircraft by increasing or decreasing air I pressure in the nosewheel tire. Level aircraft laterally by 5. Fill oil to capacity (8 quarts). placing level across center seat tracks forward of wing spar. Front seats must be in the full forward position 6. Position a 2000-pound capacity scale under each when weighing. Use leveling screws on tailcone, above of the three wheels. left side battery access door (See Figure 8-2.). 7. Level aircraft as described in Section 8-00-00 and 8-00-01 WEIGHT AND BALANCE center nose wheel. To weigh aircraft, select a level and draft free work area, 8. Weigh the aircraft. then: 9. Find reference point by dropping a plumb-bob Check for installation of all equipment as listed in from center of nose gear trunnion (retracting pivot axis) the Weight and Balance Record, SECTION VI of to floor. Mark point of intersection on floor. Reference POH/AFM. Figure 8-2. 2. Charlie Weight Installation. The aircraft, as deliv- 10. Locate longitudinal centerline of nose wheel axle ered from the factory, has correct ballast added (if any) and main wheel axles in the same manner. Mark these to compensate for installed equipment. If addition or points on floor. deletion of equipment, at a future time, affect the weight and balance of the aircraft sufficiently to require 11. Measure horizontal distance from the reference a ballast change, the proper Charlie Weight Installation pointto main wheel axle center line (Lm/r). shown on Figure 8-1 is to be used. 12. Measure horizontal distance from center line of NOTE nose wheel axle to center line of main wheel axles See Section VI of Pilot’s Operating Handbook for (Lmln). Weight and Balance reference data. 3. Ground aircraft and drain fuel tanks per SECTION 12- CPITER of GRAV[M F.S. -mm toso IOX1 looo Illo (130 (Kg) ’OK a UT -505 lom toao CEF(TER OF GRAVIM F.S.-lnches g t -553 MAUPLE: Urpiene Empty 1 weigha 251~ with CG. at 42.15 from chart thb airplane nquires -505 Charlie Wdpht Inotollotion. Far Ilcsnce eolculote ne* wsi~hf C.C. 5 Yoment 2+3~49 C: 9~’9’89 Ucsncad Empty Wdght 2363j 102781 Ucemed Empty Weight C.G. Locotlon 43.5 CHARLIE WEIGHT INSTALLATION FIGURE 8-1 REV. 10-98 8-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION 13. Record weights and measurements and compute the basic weight and CG as follows: LCIG LM/R -13 LNI a. CG Forward of Main Wheels LBS X IN. O LBS. IN. Weight Nose Distance Between Total Weight of CG Forward of Main 3 Nose Wheel Aircraft Main Wheels Axle Centers O/VN) (LM/N) <wr, (LM) b. CG Aft of Datum (Station O) Distance from center Distance from Result of computation CG (FUS STA) Nose Gear Trunnion to Nose Gear Above (a.) Distance Aft of Center of Main Wheel irunnion to Datum (Empty Axles (Horizontal) Datum Weight CG) (LMIR) (CONSTANT) (LM) (LC/G) NOTE: Empty weight includes unusable fuel and full oili(8 Qts.) and is computed with gear down and flaps up. REF,PDINT REf~ERENCE LEVEL REF, <NOSE GEAR DATUM(STA,O) (LEVELING SCREWS> TRUNNION STA, -13~ 1 1CI_3 I c/g-´•3-Lm 1/ I MEASUREMENTS Lm/r LM/R Lm/n INCHES/CM Wn Wr WI INCHES/CM WEIGHT AND BALANCE DIAGRAM FIGURE 8-2 8-00-01 REV. 10-98 Island Enterprises C H A PT E R TOVVING AND TAXIING Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 9 TOWING AND TAXIING LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT .PAGE DATE 9-Effectivity/Contents 1/2BLANK 5-94 9-00-00 3 5-94 9-30-00 4 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 9-00-00 Ground Handling .3 9-1 0-00 Towing .3 9-20-00 Taxiing .3 9-30-00 Emergency Procedures ´•3 9-EFF/CONTENTS 1/2BLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 9-00-00 GROUND HANDLING 9-10-00 -TOWING 4. Check operation of gyro instruments and turn coordinator during turns. Use a towbar for moving aircraft. The towbar attaches 5. Check engine instruments for any sluggish to nose gear crossbar. One man can move the aircraft response to engine control movements. Repair any dis- provided ground surface is relatively smooth and tires crepancies found. are properly inflated. When no towbar is available, or EMERGENCY PROCEDURES when assistance in moving aircraft is required, push by 9-30-00 hand: (1) on wing leading edges, (2) on wing tips, and 1. Engine Fire During Starting. (3) on inboard portion of propeller blades adjacent to A. Continue cranking engine with starter. propeller hub. Towing aircraft by tractor or other B. Set mixture control at IDLE CUTOFF. powered equipment is NOT RECOMMENDED. C. Turn fuel selector handle to OFF position. D. Open throttle to FULL. CAUTION E. Turn Master Switch OFF Exercise care not to turn gose wheelpast its F. Push cabin heat control OFF. normal swivel angle of 11 leg or 13- right of G. If fire is not extinguished, proceed as follows: center. Exceeding the turn limits shown on turn indicator may cause structural damage. (1) Turn electrical switches OFF. (2) Discharge fire extinguisher into engine CAUTION compartment through nose cowl openings and through Maximum allowable damage to nose gear leg lower engine cowl openings. assembly is 1/32 inch dent. (3) Call for fire-fighting equipment. 2. Fuselage or Wheel Well Fire. In case of fire in 9-20-00 WARMUP AND TAXIING wheel well (or in cabin or fuselage area), turn all fuel, Before attempting to warmup or taxi aircraft, ground electrical, and ignition controls to OFF position before personnel should be checked out by qualified pilots or evacuating aircraft to extinguish flames. other responsible personnel. 3. Electrical Fire. Circuit breakers (or circuit-breaker 1. Start and warmup engine. (Refer to POH/AFM.) switches), that automatically interrupt flow of power 2. Taxi foMlard a few feet and check brake effective- when an overload or short circuit occurs, protect all ness. electrical circuits (except the ignition-starter circuits). In 3. While taxiing, make shallow turns to test nose the event of an electrical fire, immediately turn Master gear steering. and Alternator Field switches OFF. Make sure only a fire extinguisher approved for electrical fires is used. 9-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION B LAN K 9-3eP-OQ Island Enterprises CHAPTER PA RKING, MOORING, STO RAG E, RTN TO SVC. Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 10 PARKING AND MOORING LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT .PAGE DATE 10-Effectivity/Contents 1/2BLANK 5-94 10-00-00 3 5-94 10-20-00 4 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 10-00-00 General .3 10-10-00 Parking .3 10-10-01 Storage (Flyable) .3 10-10-02 Storage (Prolonged) .3 10-10-03 Return to Service .3 10-20-00 Mooring .3 10-EFF/CONTENTS 1/2BLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 10-00-00 -GENERAL CAUTION If weight is not removed from tires, rotate The parking brake is set by applying brakes and pulling wheels/tires to a new position at least orice each out on parking brake control knob. Release parking 30 days to prevent flat-spotting tires. brake by pushing IN on parking brake control knob. 5. See appropriate TCM Service Information for en- NOTE gine preservation. There is no need to depress brake pedals to relieve pressure in brake lines during release of parking brake control. CAUTION Attach warning placards if preservation There are three tiedown points on aircraft, one on each procedures make engine inoperable. wing, outboard of main gear eiedown rings are to be threaded into built in receptacles) and tail skid/tiedown 10-10-03 RETURNING TO SERVICE fitting at aft end of tailcone. If aircraft has been stored for an extended period of 10-10-00 PARKING time, it is advisable to perform a 50-hour periodic in- When parking aircraft, place wheel chocks fore and aft spection after completion of the following preliminary of main wheels. The parking brake should be used for Steps: 1. Remove blocks from wheels. Check tire inflation. short-duration parking only. 2. Check and install batteries. CAUTION 3. Remove tape and covers from openings. Do not set parking brake when brakes are 4. Remove warning placards (if any). overheated or when cold weather could freeze 5. Replace engine oil filter. moisture and slush accumulation within the brake 6. Clean engine oil suction and pressure screens. mechanism. Do not set parking brake when aircraft 7. Clean and check oil pressure relief valve. is tied down. For madmum protection, hanger 8. Clean and check oil temperature bypass valve. aircraft during severe weather and high winds. 9. Fill engine sump with groper grade of lubricating oil. 10-10-01 STORAGE (FLYABLE) 10. Clean and reinstall engine air-inlet filter. Outdoor storage requires adequate mooring and 11. Check ignition harness. tiedown facilities. The following precautionary 12. Clean and re-gap spark plugs. measures are recommended for keeping aircraft serv- 13. Check and clean fuel injector nozzles and iceable and ready-to-fly. screens. Drain oil from fuel injector. 1. Refer to paragraph 10-20-00 for mooring instruc- 14. Check fuel tank vents for obstruction, and drain tions. sumps to remove moisture and sediment. 2. Magneto switches..........OfF 15. Complete 50-hour and preflight inspections. 3. Throttie....................CLOSED 16. See appropriate TCM Service Information for ser- 4. Mixture...........lDLE CUTOFF vicing of the engine. 5. Rotate propeller 6 revolutions every seven days; 10-20-00 MOORING STOP propeller 45 to 90 degrees from original position. 6. Keep fuel tanks filled at least one-half full to mini- When mooring aircraft out of doors: mite moisture condensation. Keep batteries fully 1. Head aircraft into the wind. charged. 2. Place chocks fore and aft of each main wheel. 7. Install protective covers over pitot head, engine 3´• Drive stakes in ground approximately three feet cowl openings, static ports, etc. outboard of each main gear and to either side of 8. Maintain a good wax finish on all exterior surfaces tailskid. (after 90 days from new paint job). 4. Install tiedown rings in wing receptacles, outboard of each main gear. Tie a 600-pound tensile strength 10-10-02 -STORAGE (PROLONGED) rope to each wing tiedown ring and anchor to ground If the aircraft is to be stored for an extended period of stake. Allow a little slack in each tiedown rope. time, the following steps are recommended for protec- tion: 5. Tie center of a rope to tail skid tiedown ring and 1. Refer to paragraph 10-20-00 for mooring instruc- anchor rope ends to ground stakes at either side of tions. tail. 2. Tape or cover all openings. 3. Remove batteries, charge fully, and store in a cool 6. For additional security, attach a rope to nose gear place. and anchor to a ground stake. 4. Raise aircraft to remove weight from tires, and 7. Lock controls by looping right front seat safety block up wheels. belt through control wheel and drawing belt snug. 10-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION B LAN K 10-20-00 Island Enterprises CHAPTER PLACARDS AND MAR KI NGS Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 11 PLACARDS AND MARKINGS LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT .PAGE DATE 11 -Effectivity/Contents 112BLANK 5-94 11-00-00 3 5-94 211-20/30-00 4 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 11-00-00 General .3 11-10-00 Markings Exterior Paint .3 11-20/30-00 Placards, Exterior/interior .3 11-EFF/CONTENTS 1l2BLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 11-00-00 -GENERAL FAA required placards and markings. 11-10-00 MARKINGS EXTERIOR PAINT Exterior paint schemes for various model year aircraft NOTE are depicted in M20R Illustrated Parts Catalog. All placards should be inspected for proper location, readability and security during 11-20/30-00 PLACARDS, EXTERIOR/INTERIOR maintenance actions. When an airplane has been painted, inspect all placards to assure that they All required placards and their locations, both interior are not obscured by paint. and exterior, are listed in Section II of the FAA Ap- proved Flight Manual and Pilot’s Operating Handbook (AFM/POH). 11-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION BLANK 11-20/30-00 Island Enterprises CHAPTER SERVICING Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 12 SERVICING LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT .PAGE DATE 12-Eff/Contents 1/2BLANK 4-95 12-00-00 3 5-94 12-10-04 4 5-94 12-20-02 5 5-94 12-20-06 6 4-95 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 12-00-00 Servicing .3 12-00-01 Servicing Intervals ´•3 12-10-00 Replenishing .3 12-10-01 Fuel Tanks ´•3 12-10-02 Fuel Drains ´•3 12-10-03 Engine Oil ´•3 12-10-04 Oxygen System ´•4 12-20-00 Scheduled Servicing ´•4 12-20-01 Induction Air Filter .4 12-20-02 Batteries .5 12-20-03 Tires Wheels ´•5 12-20-04 Brake Reservoir ´•5 12-20-05 Hydraulic Brakes ´•5 12-20-06 Cleaning .6 Rev. 4-95 12-EFF/CONTENTS 1/2BLANK Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 12-00-00 SERVICING C. After draining, be sure fuel drain valve control is returned to the closed position and the valve is not 12-00-01 -SERVICING INTERVALS leaking outside aircraft. The specified intervals (refer to Chapter 5) are con- sidered adequate to meet average requirements under WARNING normal operating conditions. It is advisable, however, During cold weather operation, frequently check to shorten service and maintenance intervals when fuel gascolator drain for ice formation by repeating operating under abnormal environmental conditions, procedures 1., A, B and C above. such as extreme temperature ranges, dusty atmos- pheric conditions, high humidity and moisture, NOTE unimproved airport facilities, or unusual operating re- If conditions conducive to fuel system icing exist, Isopropyl Alcohol may be added to fuel tanks. It is quirements. extremely important to thoroughly BLEND the 12-10-00 REPLENISHING isopropyl alcohol in with the fuel supply in FUEL TANKS quantities not to exceed 3% of the total, by volume. Keep fuel tanks at least half filled to minimize conden- 2. Defueling. Fuel tanks may be drained by one of sation and moisture accumulation in tanks. (Fuel several methods: pumping fuel out with electric boost capacity is given in Chapter 6.) pump, siphoning fuel through the filler ports, or remov- ing tank quick drain valves. WARNING Ground aircraft and fuel service vehicle during WARNING refueling. Permit no smoking or open flame within Allow no smoking or open flame within 50 feet of 50 feet of aircraft or vehicle. the defueling area. Ground aircraft and fuel container during all defueling operations. WARNING Each fuel tank is vented to the atmosphere at its A. To defues aircraft using electric boost pump: outboard aft corner vent openings are on the lower wing surface. ~heck vents for obstructions (1) Disconnect fuel line from electric boost before each flight, pump outlet at the fitting forward of the firewall. (2) Connect a flexible line to output fitting 12-10-02 FUEL DRAINS that will reach fuel receptacle. A fuel-drain valve is located in the aft inboard corner of (3) Turn fuel selector valve to tank to be each tank to provide for drainage of moisture and sedi- drained, and remove filler cap from fuel filler port. ment. Use the small plastic cup furnished with the (4) Turn boost pump ON until tank is empty. flyaway kit to drain fuel sumps. Drain wing tank sumps Repeat steps (3) and (4) to drain other tank. and gascolator before! first flight of the day and after each-fuel service to inspect for water and/or con- (5) To completely drain fuel system also tamination. Continue draining until free of water or con- drain wing tank sumps and fuel gascorator valve sump tarnination. until fuel stops running. WARNING NOTE After servicing aircraft with fuel, wait at least five When defueling using removable tank quick minutes for moisture and sediment to settle before drains, it is only necessary to remove the drains draining and checking both, the fuel tank sumps and to operate the gascolator drain. and the fuel selector valve drain. 12-10-03 ENGINE OiL 1. i=uel Gascda~or Drain. The fuel gascolator is at the lowest point in the fuel s\-,stem and has a drain Check engine oil level after engine has been stopped valve operated by a control or: the fi~or in the cabin. long enough for oil to drain back into sump. The oil To drain the fuel gascolator: filler cap access door is located in the top cowling. Any A. Switch fuel selector valve handle to L and pull lubricating oils approved by Teledyne Continental fuel drain valve control ring Bor da seconds. Motors (MHS-24) are acceptable for use after break-in B. Switch fuel selector valve handle to R and pull period. Approved products and engine oil viscosity re- fuel drain valve control ring for 10 seconds, quirements are shown in Chapter 5-20-07. 12-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CAUTION operation intervals. Use TCM filter or approved The terms "detergent", "additive", and equivalent (Champion 48109). "compounded" used in this manual are intended to When changing from mineral oil to additive oil, filter refer to a class of aviation engine lubricating) oils should be changed regardless of the operation time. to which certain substances have been added to improve them for aircraft use. These terms d~ not Check screens and filters for sludge or plugging every referto such materials commonly known as’"top 10 hours after switching from mineral oil to ashless dis- products may damage the engine and there 12-10-04 OXYGEN SYSTEM (OPTIONAL) cylinder lubricant", "dopes" and ucarbon persant (additive) oil. which are sometimes added to fuel or oil. should not be used. Under no circumsta The oxygen cylinder, when fully charged, contains ap- should automotive oil be used, since such could cause engine damage. proximately 115 cubic feet of aviators breathing oxygen (Specifications No. MIL-O-27210). Recharging of this Oil Recommendations for New-Engine or Newl~ Over- oxygen cylinder should be accomplished by using the hauled Engine Break-IN. appropriate Scott recharging fittings to the pressure New or newly overhauled engines should be operated Show" on (Figure 12-1), Pressure vs Temperature on aviation grade straight mineral oil during the first 25 Table. hours of operation or until oil consumption has, stabi- lizecs. The aircraft is delivered from Mooney with Ibroper WARNING break-in oil. Oil, grease or other lubricants in contact with OIL and FILTER CHANGING RECOMMENDATIONS oxygen create a serious fire hazard; such contact The oil and filter should be changed at 50 hour flight must be avoided when handling oxygen equipment. TEMi;aljRE .PRESSURE iEl;viPER~iljRE .PRESSURE DEGREES F PSIG .DEGREES F PSIG 0 1650 50 1875 10 1700 60 1925 20 1725 70 1975 30 1775 $8 2000 40 1825 90 2050 OXYGEN PRESSURE VS TEMPERATURE TABLE FIGURE 12-1 NOTE 12-20-00 SCHEDULED SERVICING The oxygen cylinder should not be run down to 12-20-01 INDUCTION AIR FILTER Oess than 100 P.S.I. Below this pressure,, atmospheric contamination of the cylinder n~ay The importance of keeping the induction air filter clean occur, requiring valve removal, cylinder cleaCing cannot be overemphasized. A clean filter promotes fuel and inspection at an FAA approved repair station, economy and longer engine life. The dry-type filter can usually be washed six to eight times within 500 hours or one year before replacement is necessary. NOTE To clean the dry-type induction air filter: Refer to Section 35-00-00 for periodic bottle 1. Direct a jet of air from inside of filter out. Cover pressure check. entire filter area with air jet. Any time fittings are disconnected on the oxygem sys- CAUTION tem, the threads should be treated with Do not use a compressor unit with a noule pressure greater than 100 P.S.I. to clean filter. tetrat~luoroethylene tape (hAIL-T-17720). Prior Po r;econ- nection, the system should be checked for leak$ with 2. Inspect for damage or ruptures by holding filter leak testing compound (MlL-L-25567). If no leaks are before a light or by holding light bulb inside filter. If found, wipe system clean and dry. damage is evident, replace damaged filter with new fil- ter. 12-10-04 Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL NOTE CAUTION If filter shows an accumulation of carbon, soot, or Do not fill reservoir while parking brake is set. oil, continue with cleaning steps 3 through 5. Use only hydraulic fluid (red), per specification MIL-H- 3. Soak filter in non-sudsing detergent for 15 5606. Do not fill reservoir higher than two inches below minutes. Agitate filter back and forth for two to five filler port. minutes to free filter element of deposits. 12-20-05 HYDRAULIC BRAKES (Bleeding) 4. Rinse filter element with a stream of clean water until rinse water is clean. 5. Dry filter thoroughly. Do not use light or air above CAUTION 1800 F. for filter drying. Fluid in the wheel cylinders may be under high 6. Check alternate air door for proper operation and pressure due to heat or expansion. Therefore, be sure parking brake is released prior to beginning sealing. hydraulic system servicing. 7. Reinstall filter in aircraft. Make sure of proper seal- ing and security. For best results, use a hydraulic pressure service unit 12-20-02 BATTERIES (pressure pot) to back bleed the system through wheel Service batteries with distilled water to maintain cylinder bleeder valves. electrolyte above plates. After adding water in freezing SINGLE BRAKE SYSTEM (PILOTS SIDE ONLY) weather, charge battery long enough to mix electrolyte 1. Remove hydraulic fluid reservoir filler plug, and in- and water. Keep battery electrolyte above a specific stall a suitable fitting for attaching a flexible drain line. 2. Immerse open end of drain line into a hydraulic gravity of 1.225 to avoid freezing. fluid container or catch container containing MIL-H- To service battery(ies): 1. Remove battery caps. Check electrolyte and ser- 5606 fluid. 3. Attach pressurized hydraulic fluid service unit to vice battery as required. wheel cylinder bleeder valve and open valve. Hydraulic service unit should be free of air prior to servicing CAUTION Battery gases may be explosive. aircraft system. 4. Feed fluid from service unit into brake system. Check for air bubbles at end of drain line immersed in 2. Check battery mounting area for corrosion and fluid. spilled electrolyte. To clean cables, terminals, mounting area and battery case, use a solution of bicarbonate of 5. When fluid is flowing, slowly depress pilot’s brake soda and clean water to neutralize corrosion and pedal by hand and slowly release. Repeat three (3) to four (4) times. spilled electrolyte. 6. Allow fluid to flow until clear of air bubbles. 7. Close wheel cylinder bleeder valve; remove ser- CAUTION vice line. When cleaning, do not allow bicarbonate of soda to enter battery cells permanent damage will result if soda mixes with electrolyte. NOTE Brake pedal may need to be pulled back in order 3. Rinse battery with clean water. Wipe clean with a for fluid to bleed back into reservoir. dry cloth. 8. To bleed opposite brake, (single brake system 4. To retard corrosion, coat terminals with petroleum jelly after cleaning and tightening them, only) repeat steps 3 through 7. 5. Check battery vent line lines for obstructions, line IF DUAL BRAKES AND SHUTTLE VALVE ARE IN- STALLED kinks, etc. 1. While pressurized hydraulic fluid service unit is 12-20-03 TIRES AND WHEELS still attachedto either wheel cylinder bleeder valve. Keep tires at recommended air pressure. (Refer to 2. Loosen co-pilot’s brake line at shuttle valve. Pro- Chapter 6-00-01. vide another catch container. 1. Check tires for wear, cuts and bruises. 3. Restrict (stop) outflow from reservoir drain line to 2. Check valve stems for evidence of tire slippage or catch container. pulling. 4. Allow fitting to remain loose until fluid is clear of 3. Check wheels for damage. air bubbles as it drains from shuttle valve fitting into 4. Check wheel bearings for condition and lubrica- catch container. tion. 5. When clear, tighten co-pilot line fitting and remove restriction from reservoir drain line. 12-20-04 BRAKE RESERVOIR 6. Stroke co-pilot’s brake pedal several times and Frequently check brake reservoir for proper fluid level. allow any purged air to exit through reservoir. See Chapter 12-20-05 for location. See Section 5-20-07 7. Shut off bleeder valve at wheel cylinder; remove for proper fluid. fluid pressure unit. 12-20-02 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION 8. To bleed opposite brake, (dual brake sWstem) 2. WINDSHIELDS, WINDOWS AND DOORS repeat steps 2 through 8. A. Flush windshield and windows with water prior 9. Remove drain line from reservoir, to wiping. Never wipe while dry. REPLENISH HYDRAULIC RESERVOIR TO OP~RAT- B. Remove grease or oil with a soft cloth ING LEVEL saturated in kerosene. 1. Lower fluid level in reservoir to two inches;below filler port. CAUTION 2. Reinstall filler plug. Never use gasoline, benezene, carbon 3. Check brake linings for excessive wear and tetrachloride, acetone, fire extinguisher fluid, proper installation. Refer to Section 32-40-04 for /Brake de-icer fluid, lacquer thinner, or household window Removal and Inspection Procedures. cleaning sprays on windows or windshields. Such 4. Depress brake pedals to check for spon~iness. solvents will soften or craze the plexiglas surface. Resistance should be solid and even when ibrake C. Clean windows and windshields with an antl- pedals are depressed, static plexiglas cleaner. 12-20-06 CLEANING D. Check door seals for damage that could cause leakage. Cleanliness is a major prerequisite to adequate proper workingorder.E. Check cabin and baggage door mechanism for tion and maintenance of an aircraft. Cleanliness ces the appearance of an aircraft and reduce/s the probability of corrosion. NOTE 1. EXTERIOR Minor scratches or abrasions may be polished out A. Before washing aircraft exterior, cover .brake by using plexiglas re-surfacing kits, ie, discs, pitot head, and static ports. Micro-Mesh, available from aircraft accessory B. Flush away loose dirt and mud. suppliers. C. Wash exterior with a mild aircraft deterg~nt in cool water and a soft cleaning cloth or chamois- /Rinse 3. ENGINE COMPARTMENT Accumulation of dirt away soap film. and oil within the engine compartment creates a fire hazard and hampers inspection procedures. CAUTION A. Wash engine cowling and engine compartment down using a non-fiammable solvent. Do not use so called "mild" household deterg(ents to wash aircraft exterior. Such detergents mby B. Dry engine cowling and engine compartment after washing. damage finish and corrode aluminum com onents. 4. CABIN INTERIOR CAUTION Use normal household cleaning practices for routine in- Do not apply wax or use pre-wax cleaners d._ullZg terior care. initial paint curing period. Use only mild a A. Frequently vacuum seats, rugs, upholstery detergent and cool water when washing exteiior pa"els and headliners to remove surface dust and dirt. during the first 90 days after repainting. B. Clean interior components with cleaners shown below. Use soft cloth to apply. Dry with soft, dry D. To remove heavy oxidation film, use a pre-wax cloth. cleaner. (1) Leather Leather cleaner. E. Apply an exterior-finish wax recommended for (2) Vinyl Vinyl cleaner. protection of urethane enamel. Apply a heavy cdating (3) Izit Leather Wool windowlupper side material of wax to leading edges of wings, empennagei and Woolite (3 parts H2O to 1 part Woolite) nose section to reduce drag and abrasion. (4) Carpet Carpet cleaner (See CAUTION below) CAUTION CAUTION When fuel, hydraulic fluid, or other fluid Never apply household cleaners to interior dye is spilled on painted surfaces, remove it/at furnishings. Do not use alcohol or strong solvents once to prevent staining. Flush away spilled on interior plastics. When using commercial battery electrolyte immediately with water. T cleaning and finishing compounds, carefully follow exposed area with bicarbonate of soda solutibn manufacturer’s instructions. Never saturate fabrics followed by thorough washing with a mild airojraft or carpet with solution which could damage detergent solution. backing and padding materials. To minimize wetting of carpets, keep foam as dry as possible and rub in circles. Use a vacuum cleaner to F. Blow moisture away from areas that mayi trap remove foam. Do not allow carpets to remain accumulate water, IE. engine mount atfirewall attach damp; dry them thoroughly.points (inside cupped portion of tubing). 12-20-06 6 Rev 4-95 Island Enterprises CHAPTER STANDARD PRACTICES (AIRFRAME) Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORPORATION CHAPTER 20 STANDARD PRACTICES AIRFRAME LIST OF EFFECTIVE PAGES CHAPTER SECTION SUBJECT ´•PAGE DATE 20-Effectivity/Contents I12BLANK 5-94 20-00-00 3 5-94 20-00-01 4 5-94 20-00-02 5 5-94 20-00-02 6 5-94 20-00-03 7 5-94 20-00-03 8 5-94 TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE 20-00-00 General .3 20-00-01 Skin Specifications .3 20-00-02 Corrosion Detection and Prevention .5 20-00-03 Painting .7 20-EFF/CONTENTS 11/2BeANI~ Island Enterprises MOONEY AIRCRAFT CORPORATION M20R SERVICE AND MAINTENANCE MANUAL 20-00-00 GENERAL tification. Advisory Circular 43.13-1( outlines inspec- tion and repair practices acceptable to the F.A.A. Ad- This chapter of the manual discusses treatment of ministrator. metal surfaces for corrosion control and the identifica- tion of skin panels for replacement purposes. Those 20-80-01 SKIN SPECIFICATIONS who inspect or repair aircraft should consult FAR 43, Maintenance, Preventive Maintenance, Rebuilding and Alteration and Sub Parts A, D and E of FAR 65, Cer- 6 r5 r4 r3 STA I I STA I STA I STA I STA 210~971 1 147,75 1 103,50 1 59,25 24~50 STA 193~50 18 15 19 13 12 17 11 10 I 14 --J L9 WING SKIN PANELS INDEX- SKIN .MATERIAL INDEX SKIN MATERIAL NO. THICKNESS NO. .THICKNESS 1. 0.063 2024 T-3 CLAD 12. 0.025(c) 2024 T-3 CLAD 2. 0.050 2024 T-3 CLAD 13. 0.020(a) 2024 T-3 CLAD 3. 0.040 2024 T-3 CLAD 14. 0.032 2024 T-3 CLAD 2024 T-3 CLAD 6. 0.025 2024 T-3 CLAD 17. 0.016 2024 T-3 CLAD 4. 0.040 2024 T-3 CLAD 15. 0.040 5. 0 025 2024 T-3 CLAD 16. 0.040 2024 T-3 CLAD 7. 8.832 2324 T-3 CLAD 18. 0.050 2024 T-3 CLAD 8. 0.848 21124 T-3 CLAD 19. Polyester Glass-Fiber keinforced 9. 0.025 2024 T-3 CLAD 10. 0.625 2024 T-3 CLAD 11. 0.025 2024 T-3 CLAD (a) Same thickness on top and bottom. (b) Top of wing only. (c) Top aft flap skin that section). (d) Top inboard flap skin. WING SKIN PANELS FIGURE 20-1 28-00-00 Island Enterprises SERVICE AND MAINTENANCE MANUAL M20R MOONEY AIRCRAFT CORBORA’610M STA 14 7 6 7 7 ~1 ’A -5.375 6-\ 5-7 11 4~ 3 STA 3,68 r~ o 1~ 10 -J I I I I I I I I I I I 11 STA STA STA STA SIA STA STA ~fr,50 1 176,00 114~,OO 1 100,00 i 53,00 iT1~80 -5´•00 9 L 4 5 1 R’3 L 5 FUSELAGE SKIN PANELS SMM20-2 INDEX SKIN .MATERIAL INDEX SKIN MATERIAL NO. THICKNESS NO. .BHICKNESS 1. 8.025 2024 T-3 GLAD 1(P. 0.032 2024 T-3 CLAD 2. 0.640(d) 2024 -0 GLAD 11. 0.032 2024 83 CLAD 3. .0.025(c)(b) 2024 T-4 CLAD 12. 8.032 2024 8-3 CLAD 4. 0.025 2024 T-3 CLAD 13. 0.025(a) 2024 T-3 CLAD 5. 0.025(b) 2024 T-3 CLAP 14. Polyester Glass-Fiber Reinforced 6. 0.020 2024 T-3 CLAD 7. 0.025 2024 T-3 CLAD 8. .0.032(d) (e) 2024 -0 CLAD 9. 0.025 2024 T-3 CLAD (a) Left side only. (b) Right side only. (c) 0.032 can be used. (d) Heat treated to T-42 condition after forming. (e